session IP

Title: Interactive Presentations
Date: 2015-10-14
Time: 13:15

IPC members

Coordinator: Mr. Giorgio Saccoccia, Italian Space Agency (ASI), Italy;
Coordinator: Mr. Richard Blott, British Interplanetary Society, United Kingdom;
Coordinator: Dr. Toru Shimada, Institute of Space and Astronautical Science (ISAS), Japan Aerospace Exploration Agency, Japan;
Coordinator: Dr. Helen Webber, Reaction Engines Ltd., United Kingdom;

papers
Order	Paper title	Presentation status	Speaker	Affiliation	Country
1	space gates: repurposing the mini-magnetosphereic plasma propulsion system as a mass driver	confirmed	Mr. Zachary Riffle		United States
2	Aerothermodynamic experiment and simulation of spatial effects in a divert thrust chamber in hypersonic flow	confirmed	Prof. Wen-lu Zhou	Beijing Aerospace Propulsion Institute	China
3	the micro thrust automatic measurement system of plasma thruster		Mrs. jing li		China
4	Design and Structural Characteristics of Gas Gimbaling Apparatus in LOX/Kerosene Rocket Engine	confirmed	Dr. Fu Ping	Xi'an Aerospace Propulsion Institute	China
5	Ground testing of low-thrust self-pressurized hybrid motor		Dr. Olexiy Shynkarenko	University of Brasilia	Brazil
6	quasi-direct numerical simulation on atomization and mixing characteristics of a pair of impinging jets	confirmed	Mr. Jianan Li	The 11st Institute of the Sixth Academy, China Aerospace Science and Technology Corporation (CASC)	China
7	Feasibility Study on Non-Toxic Hypergolic Bipropellant Thruster using Hydrogen Peroxide as an Oxidizer	confirmed	Mr. Hongjae Kang	Korea Advanced Institute of Science and Technology (KAIST)	Korea, Republic of
8	Gas-phase nuclear rocket engines and propulsive mass for them.	confirmed	Mr. Oleg Aleksandrov	AVIASTAR Inc www.aviastar.us	United States
9	fundamental energy propulsion systems	confirmed	Mr. Leon Africa		South Africa
10	numerical simulation of grain's dynamic regression process for n2o/htpb hybrid rocket motors	withdrawn	Mr. Yu Zhao	Shanghai Academy of Spaceflight Technology (SAST), China Aerospace and Technology Corporation (CASC)	China
11	experimental simulation investigation of diaphragm rupture and washing for rocket engine in arc heated air flow	confirmed	Mrs. Cheng Meisha	CASC	China
12	Improved method for PIV measurement on high temperature vitiated supersonic flow-field	confirmed	Dr. Xi Wenxiong	State key laboratory of laser propulsion & application, Equipment Academy of PLA, Beijing, China	China
13	Research on Discharge Plasma Characteristics of An Ablative Pulsed Plasma Thruster via Emission Spectrometry	withdrawn	Dr. Lei Yang	China Academy of Launch Vehicle Technology(CALT)	China
14	Verification of The Venus Technological Mission Module	confirmed	Mr. Jacob Herscovitz	RAFAEL	Israel
15	Pocket Rocket: A radio-frequency electrothermal plasma micro-thruster	withdrawn	Ms. Amelia Greig	Australian National University (ANU)	Australia
16	Frequency Behavior of Liquid Fueled Ramjet with variable area nozzle	confirmed	Ms. Qin Yan-ping	Xi'an Aerospace Propulsion Institute	China
17	wall temperature prediction of regenerative cooled rocket engine based on a coupled heat transfer model	confirmed	Mr. Guangxu Wang	The 11st Institute of the Sixth Academy, China Aerospace Science and Technology Corporation (CASC)	China
18	Solar Thermal Propulsion Review	withdrawn	Dr. Marc M. Cohen	Astrotecture™	United States
19	Electro-Magnetic Vacuum Thrust Producers (EMVTP)	confirmed	Mr. Vladimir Shirin		Kazakhstan
20	investigation of flow induced pressure difference during high altitude simulation	confirmed	Mr. Jianwen Yang	National Key LAB of Science and Technology on LRE	China
21	Numerical Study for Simulating Liquid Rocket Engine Exhaust Plume Using Multi-species Un-reacted Flow Model	confirmed	Dr. Sunil Kang	Korea Aerospace Research Institute (KARI)	Korea, Republic of
22	parametric study and sensitivity analysis of hybrid rocket motors with double-tube configuration	confirmed	Mr. Arnau Pons Lorente	School of Astronautics, Beihang University	China
23	design and performance evaluation of hydrogen peroxide oxidizer hybrid thruster for sounding rocket system	withdrawn	Mr. Minwoo Lee	Satrec Initiative	Korea, Republic of
24	analysis of system damping effect on time-lag based combustion instability model	confirmed	Mr. Guangxu Wang	National Key LAB of Science and Technology on LRE	China
25	Analysis of a Magneto-hydro-dynamic (MHD) Oblique Detonation Wave Engine	confirmed	Dr. Kongqian Sun	Science and Technology on Scramjet Laboratory,Beijing Power Machinery Research Inst	China
26	LIP's electric propulsion developments for chinese satellite platform	confirmed	Prof.Dr. tianping zhang	Lanzhou Institute of Physics	China
27	propellant-less propulsion system using microwaves	confirmed	Mr. Pradeep Mitra		India
28	Thermal Test on an Ion Thruster	confirmed	Mr. XINQUAN QIAO	Institute of Spacecraft System Engineering,China Academy of Space Technology (CAST)	China
29	Experimental Investigation of Influencing Factors for Reliable Startup and Steady Work of 20W Microwave Electromal Thruster under Realistic Space Conditions	confirmed	Mr. Rohan M Ganapathy	Hindusthan College of Engineering and Technology	India
30	Innovative space propulsion technology using vacuum arc thrusters	withdrawn	Mr. Jonathan Lun	DENEL Spaceteq	South Africa
31	INTERSTELLAR MISSION TO BARNARD'S STAR USING ADVANCED NUCLEAR PROPULSION METHODS	confirmed	Dr. Ugur Guven		United States
32	Theoretical modeling of the combustion of gel fuel droplets	confirmed	Prof. Benveniste Natan	Technion – Israel Institute of Technology	Israel
33	SPACE QUALIFICATIONS OF THE MEMS-BASED SOLID PROPELLANT THRUSTER ARRAY FOR ON-ORBIT VERIFICATION USING CUBE SATELLITE		Mr. Sung-Hyeon Han	Republic of Korea	Korea, Republic of
34	Three gridded ion engines for future high power electric propulsion missions	confirmed	Prof. Stephen Gabriel	University of Southampton	United Kingdom
35	a novel design of mems based micropropulsion system for a nanosatellite	withdrawn	Mr. Jammalamadaka Mani Sai Suryateja	Birla Institute of Technology and Science(BITS)	India
36	Validation with CFD Simulations of a Simplified Model of a Hybrid Rocket Motor	confirmed	Mr. Florin Mingireanu	Romanian Space Agency (ROSA)	Romania
37	experimental study of flow separation in a subscale parabolic contour nozzle	withdrawn	Dr. yibai wang	Beijing University of Aeronautics and Astronautics (BUAA)	China
38	sliding mode control control for hypersonic flight vehicle with time delay estimation and compensation	confirmed	Dr. xiao hanshan	China Aerodynamics Research and Development Center (CARDC)	China
39	development of a low power cylindrical hall thruster propulsion system for microsatellites	withdrawn	Mr. Nathan Orr	Space Flight Laboratory, University of Toronto	Canada
40	Performance and environmental test results of a novel electric propulsion technology for small satellites	withdrawn	Dr. Natalya Brikner		United States
41	"Low Power Hall Effect Thruster Activities at Sitael"	confirmed	Dr. Tommaso Misuri	Sitael Spa	Italy
42	Improved Modeling of Electric Sail (E-sail) Force Generation	confirmed	Mr. Thomas Gemmer	North Carolina State University	United States
43	Development of Low Power Electric Propulsion System for Micro-Satellites	confirmed	Mr. Gal Alon	Rafael Advanced Defense Systems Ltd.	Israel
44	An Overview of Hollow Cathodes Activities at Sitael	confirmed	Dr. Riccardo Albertoni	Sitael Spa	Italy
45	Performance increase of liquid rocket motor through pump modification for higher injection pressure operation	confirmed	Mr. Florin Mingireanu	Romanian Space Agency (ROSA)	Romania
46	"MEPS: Programme Overview and System Development Status"	confirmed	Dr. Tommaso Misuri	Sitael Spa	Italy
47	Development of a kW-level plasma thruster in project SAPERE –STRONG	confirmed	Prof. Daniele Pavarin	CISAS – “G. Colombo” Center of Studies and Activities for Space, University of Padova	Italy
48	Microthruster development for trajectory correction on upper stages and satellites	confirmed	Mr. Florin Mingireanu	Romanian Space Agency (ROSA)	Romania
49	towards green propulsion for next-generation rockets with han-based monopropellants		Mr. JUN LIU	Shanghai Institute of Space Propulsion	China
50	Central binary collision of power-law model gel propellant droplets: effects of n and K on maximum deformation	withdrawn	Dr. Zejun Liu	PLA Information Engineering University	China
51	Development of a Moveable Sleeve Injector with a Fixed Pintle for a Throttleable Rocket Combustor	confirmed	Prof. Jaye Koo	Korea Aerospace University	Korea, Republic of
52	A simple design for ablative liquid-fed pulsed plasma thrusters for small satellites	withdrawn	Dr. William Yeong Liang Ling	University of Tokyo	Japan
53	Low Frequency Combustion Instability Characteristics of Polyethylene-N2O Based Hybrid Rocket Motor	confirmed	Prof. Artur Bertoldi	University of Brasilia	Brazil
54	design optimization of a RBCC ejector mode using entropy analysis	confirmed	Dr. yuntao zheng	Science and Technology on Scramjet Laboratory, Beijing Power Machinery Research Institute	China
55	Propulsion System of the Lunar Lander built for Google Lunar X Prize	confirmed	Mr. Nakul Kukar		India
56	Solid rocket motor burn simulation considering complex 3D propellant grain geometries	confirmed	Mr. Guilherme Mejia	Instituto Tecnológico de Aeronáutica (ITA)	Brazil
57	Experimental insight into the effect of sound intensity on smoldering combustion	confirmed	Mr. vinayak malhotra	Indian Institute of Technology	India

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